Overall Performance Analysis–Oriented Aerodynamic Configuration Optimization Design for Hypersonic Vehicles

Fan, Ding; Zihan, Jiao; Chen, Jun; Zhang, Dong; Tang, Shuo

doi:10.2514/1.a33729

Cited by 10 publications

(4 citation statements)

References 22 publications

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“…Wuilbercq et al [12] use reduced-order models to compute aero-thermal, heat protection, and propulsive characteristics, with the inclusion of mass estimation for reusable hybrid vehicles in both ascent and re-entry flight regimes. Overall performance of hypersonic vehicles is taken into account by Deng et al [13], coupling flight characteristics and geometric performance parameters within objective functions. Recently, Di Giorgio et al [14] introduced an aerothermodynamic design optimization framework for hypersonic vehicles.…”

Section: A Brief Review Of Super-hypersonic Vehicle Optimizationmentioning

confidence: 99%

Creation of Design and Analysis Tools for Large Design Space Reusable Launch Vehicle Shape Optimization

Cusick

Kontis

2019

AIAA Aviation 2019 Forum

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A design optimization suite currently under development for arbitrary super-hypersonic vehicles is introduced. A brief review of literature on the subject is presented. Parameterization techniques utilized to obtain realistic geometries of various flying components are discussed. Well known engineering methods for the prediction of inviscid high speed aerodynamic coefficients are outlined, alongside implementation of streamline tracing and mesh interpolation for the calculation of viscous and local condition dependent approaches. Global optimization methods are employed, with detailed discussion on the specific characteristics chosen for this work. Validation cases are presented for the aerodynamic module, comparing computed results to wind tunnel tests gathered in previously published research. An overview of the optimization loop is provided, followed by an aerodynamic design optimization, demonstrating the potential of the combined methodologies.

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Section: A Brief Review Of Super-hypersonic Vehicle Optimizationmentioning

confidence: 99%

Creation of Design and Analysis Tools for Large Design Space Reusable Launch Vehicle Shape Optimization

Cusick

Kontis

2019

AIAA Aviation 2019 Forum

View full text Add to dashboard Cite

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“…Authors in [23] have proposed the optimal design of hypersonic vehicle which has been achieved by using an accurate surrogate-based optimization method. Numerical single-discipline optimization problem has been solved in DIRECT global optimizer.…”

Section: Introductionmentioning

confidence: 99%

Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating

Vidanović

Rašuo

Kastratović

et al. 2020

Journal of Spacecraft and Rockets

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“…The lift-to-drag ratio of multi points are optimized by multi-objective optimization method with volume and lift as constraints, hypersonic engineering methods (HEM) was used to estimate aerodynamic characteristics, the results show the application potential of 3D multi-block CST method in the design of hypersonic vehicle. Deng et al [12] used the quadratic curve method to establish a parametric model of HTV-2 type configuration. After parameter sensitivity analysis, Navier-Stokes (N-S) equations were solved based on ANSYS Fluent, aerodynamic shape optimization method based on surrogate optimization was established and wind tunnel verification test was carried out, the test result proves the effectiveness of the optimization method.…”

Section: Introductionmentioning

confidence: 99%

Rapid Aerodynamic Shape Optimization With Payload Size Constraints for Hypersonic Vehicle

2019

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Nowadays, aerodynamic shape optimization of the hypersonic vehicle is mostly optimized for local details such as the wing. In the overall shape optimization, the conceptual design of the vehicle is more common, in which the shape is described in fewer parameters and optimized roughly. Meanwhile, in the optimization, the capacity is considered only by the volumetric ratio, and it can hardly meet the actual payload size constraints, which is difficult to apply to engineer practice. In this paper, a rapid aerodynamic shape optimization method with payload size constraints is proposed. The analytic method combined with a clamped cubic spline curve is used to establish the parametric model with the payload size constraints. In order to ensure the accuracy and improve the optimization efficiency, the aerodynamic characteristics of the vehicle are quickly obtained based on the adaptive Cartesian grid generation method and viscosity modified Euler equations. The lift-to-drag ratio is used as the objective, and a sequence iteration method with multi-point selecting strategy is adopted to make convergence faster. In order to compare and verify the effectiveness of the proposed method, the optimal solution is compared with a reference shape obtained through a conventional multi-objective aerodynamic shape optimization with lift-to-drag ratio and the volumetric ratio as objectives. Through comparative analysis, the method proposed in this paper can find the optimal shape that satisfies the payload size constraints quickly, which can effectively improve the aerodynamic performance of the hypersonic vehicle and can be better applied to practical engineering optimization problems.INDEX TERMS Hypersonic, parametric design, surrogate model, computational fluid dynamics, optimization.

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Overall Performance Analysis–Oriented Aerodynamic Configuration Optimization Design for Hypersonic Vehicles

Cited by 10 publications

References 22 publications

Creation of Design and Analysis Tools for Large Design Space Reusable Launch Vehicle Shape Optimization

Creation of Design and Analysis Tools for Large Design Space Reusable Launch Vehicle Shape Optimization

Multidisciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating

Rapid Aerodynamic Shape Optimization With Payload Size Constraints for Hypersonic Vehicle

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